Methods of retracting a strut assembly for stowing aircraft landing gear comprise longitudinally translating an upper bulkhead within an upper tubular housing from a lower position to an upper position by pressurizing an upper bulkhead space between an upper plate of the upper bulkhead and an upper bulkhead restriction structure that is fixed to the upper tubular housing. Other methods of retracting a strut assembly for stowing aircraft landing gear comprise flowing liquid from an upper liquid chamber positioned above an upper bulkhead within an upper tubular housing to a recoil chamber, wherein during the flowing, the liquid is prevented from passing from the recoil chamber to a pressure chamber that is defined between the upper bulkhead and a lower bulkhead, thereby longitudinally translating a lower tubular housing upward.

Methods of retracting a strut assembly for stowing aircraft landing gear comprise longitudinally translating an upper bulkhead within an upper tubular housing from a lower position to an upper position by pressurizing an upper bulkhead space between an upper plate of the upper bulkhead and an upper bulkhead restriction structure that is fixed to the upper tubular housing. Other methods of retracting a strut assembly for stowing aircraft landing gear comprise flowing liquid from an upper liquid chamber positioned above an upper bulkhead within an upper tubular housing to a recoil chamber, wherein during the flowing, the liquid is prevented from passing from the recoil chamber to a pressure chamber that is defined between the upper bulkhead and a lower bulkhead, thereby longitudinally translating a lower tubular housing upward.

Disclosed is an aircraft piston assembly, having: a piston housing fluid port formed in a piston housing; a piston shaft, disposed within the piston housing, configured for translation in either forward or aft directions when fluid is respectively supplied to or removed from the piston housing; a screw shaft, disposed within the piston housing, that includes a first gear that rotates without translation while the piston shaft translates; and a slider, disposed within the piston housing, that includes a second gear, and that is configured for translation without rotation, wherein: the slider moves between a first position where the first gear and the second gear are separated from one another to allow the piston shaft to translate and a second position where the second gear surrounds the first gear so that the first and second gears are engaged with one another and the piston shaft is prevented from translating.

An emission-capturing apparatus includes a tank having an inlet and an outlet. The apparatus further includes a muffler fluidly coupled with the outlet to intercept fluid exiting the outlet, permit passage of gas through the muffler, and inhibit passage of liquid through the muffler. The apparatus further includes a hose having a tank end and a distal end. The tank end is coupled to the inlet. The apparatus further includes a fitting fluidly coupled to the distal end of the hose. The fitting is configured to be fluidly coupled to an end section of an ejection port of a vehicle to receive an emission from the ejection port.

An emission-capturing apparatus includes a tank having an inlet and an outlet. The apparatus further includes a muffler fluidly coupled with the outlet to intercept fluid exiting the outlet, permit passage of gas through the muffler, and inhibit passage of liquid through the muffler. The apparatus further includes a hose having a tank end and a distal end. The tank end is coupled to the inlet. The apparatus further includes a fitting fluidly coupled to the distal end of the hose. The fitting is configured to be fluidly coupled to an end section of an ejection port of a vehicle to receive an emission from the ejection port.

An upper side brace for use in landing gear includes a main body having a mounting end configured to be proximal to an aircraft and a lower end configured to be proximal to a lower side brace. The upper side brace further includes an unlock actuator cylinder formed monolithic with the main body and configured to house a piston to form an unlock actuator.

An upper side brace for use in landing gear includes a main body having a mounting end configured to be proximal to an aircraft and a lower end configured to be proximal to a lower side brace. The upper side brace further includes an unlock actuator cylinder formed monolithic with the main body and configured to house a piston to form an unlock actuator.

An aircraft assembly having: a first part; a second part, the second part being movably mounted with respect to the first part; an electro-hydraulic actuator coupled between the second part and a first anchor point, the actuator comprising a cylinder defining a bore and a piston and rod assembly slidably mounted within the bore and an active chamber within which an increase in fluid pressure causes the actuator to change during a first phase between first and second extension states to move the second part relative to the first part. The electro-hydraulic actuator further includes a hydraulic fluid supply circuit comprising a piezo-electric pump operable to supply pressurised fluid to the active chamber to change the actuator between first and second extension states.

An aircraft assembly having: a first part; a second part, the second part being movably mounted with respect to the first part; an electro-hydraulic actuator coupled between the second part and a first anchor point, the actuator comprising a cylinder defining a bore and a piston and rod assembly slidably mounted within the bore and an active chamber within which an increase in fluid pressure causes the actuator to change during a first phase between first and second extension states to move the second part relative to the first part. The electro-hydraulic actuator further includes a hydraulic fluid supply circuit comprising a piezo-electric pump operable to supply pressurised fluid to the active chamber to change the actuator between first and second extension states.

A thermal actuator includes a piston slidingly within a cylinder. The piston cooperates with the cylinder to define a cavity. The piston also includes a rod extending away from the cavity. A magnetic field generator selectively imparts an alternating magnetic field to the cylinder, and inductively heats a heating element mounted within the cavity. The cavity also includes a volume of a phase-change material, which is melted by the heating element. The melting phase-change material expands to drive the rod from a retracted position to an extended position.